Elastic-fluid turbine.



ELASTIC FLUID TURBINE. APPLICATION PILED 001229, 1904.

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Witwzoow /l F P-" No. 825,164. PATENTED JULY 3, 1906.

E. TAYLOR. ELASTIC FLUID'TURBINE.

APPLIGATION FILED 00m 1904.

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E in 721 702" No. 825,164. PATENTED JULY 3, 1906. B. F. TAYLOR. ELASTICFLUID TURBINE.

APPLICATION FILED 00129. 1904.

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uvzntoz Edwr'nf'jybr M, M $25 No. 825,164. PATENTED JULY 3, 1906. B. P.TAYLOR.

ELASTIC FLUID TURBINE.

APPLICATION FILED 00T.29.1904.

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lnuenfoz Edw/n 1? 7215/0)" q/vifneoaea FILE-- '7 2 No. 825,164. PATENTEDJULY 3, 1906. B. F. TAYLOR. ELASTIC FLUID TURBINE.

APPLICATION FILED OCT.29. 1904.

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Jnvmfloz Edwin 721 /1 EDWIN F TAYLOR, OF /VYNOOTE, PENNSYLVANIA.

ELASTIC-FLUID TURBINE.

Specifi'cationof Letters Patent. Application filed October 29. 1904.Serial No. 230.536.

Patented July 3, 1906.

l condition. From this state the fluid is again To all whmizit mayconcern;

Be it known that I, EDWIN F.' TAYLOR, a

citizen of the United States, residing at Wyna cote, in the county ofMontgomery and State of Pennsylvania, have invented certain new anduseful Improvements in Elastic-Fluid Turbines; and I do herebydeclarethe folj lowing to be a full, clear, and exact description of theinvention, such as will enableothers skilled in the art to which itapper tains to make and use thesame.

This invention, which relates to elasticfluid turbines, contemplatescertain new and useful improvements designed more especially foremployment in-connection with the constructions of turbines for whichLetters Pat-' ent numbered 752,602, 752,603, and 752,604

were issued to me on or about the 16th day of 1904; It is to beunderstood, however, that the present improvements are equally, capableof utilization in connection with other existing turbine constructionsand no limitation is intended by the refernce to my patents above noted.Neither do I I limit the application of the improvementsto anyparticular class ofturbine, although I hive illustrated and describehereinafter a multiple-wheel engine of the impact-reaction typeembodying the present novel and useful features of construction.

Referring to my patented constructions above noted, it is patent thatthe motive fluid therein is expanded through a series of nozzle-sectionsand creates impact and reactive forces on blades or buckets carried bymoving'parts located alternately between the successive nozzle-sections,which nozzle sections are so proportioned that an adiabatic partialexpansion of the fluid may be effected in each section of the completenozzle. The kinetic force of the fluid due to such expansion isaccelerated at the point of impact through a change in entropy of thefluid immediately following its release from the noz,

zle-section and yields up its heat on the moving part in proportion tothe degree of expansion created in the nozzle-section. The fluid havingthus performed work through the me dium of the power-transmitting shaftby giving up its heat through impact in proportion to the degree of itsexpansion, assumes-a temperature corresponding "to the remainin pressuremaintained and is again in a norma adiabatically partially expandedthrough a succeeding nozzle-section, the degree of this expansioncorresponding to that of the previous expansion, and substantially thesame degree of heat, together with substantially the same amount ofenergy, is therefore applied in the second stage, and so on through* outthe range, all of the nozzle-sections bein constructed and arranged todeliver an equa amount of energy on each moving part of the series andto effect a continuous adiabatic expansion of the motive fluid. Thedegree of expansion of the fluid efiected in the nozzle-sections isdetermined by the velocity of and the degree of heat from the fluidrequired for the impact on the moving part, the nozzle-sections beingproportioned to obtain the desired result. For example, in a highspeedturbine a lesser number of nozzle-sections are required, but saidsections are necesf sarily proportioned to create an adiabatic partialexpansion of the fluid to a lower presmanded in a slower-velocityturbine. It will of course be understood that a speed corresponding tothe highest theoretical efliciency is to be-desired. Neverthelessturbines can be constructed along the stated lines to have Wide rangesof velocities with but slightlyimpaired efficiency.

One of the most difficult problems presented in turbine work is to notonly maintain the efliciency throughout the range of load, but toconstruct a variable-speed turbine and maintain in its operation atvarious speeds sub-- stantially the same degree of efficiency.

- The present invention contemplates, among other valuable featureshereinafter referred to and described, elements alternately active tocreate and to direct different degrees of energy against the moving part'of the'tu'rbine. Said elements may each-consist of a nozzle or grou ofnozzles capable of creating a degree of uid expansion differing fromthat created in the nozzle or group of nozzles constituting the otherelement, the differential elements commonly communicating with afluidsupply and being alternately active to deliver varying kineticforces against the impactsurfaces of the movable part, whererco by saidpart is caused to rotate at a greater or less speed, dependent upon therequire The shaft is mounted at one end in a journal ments. It will beunderstood from the foregoing that the passage of the fluid is cut offfrom the one group of nozzlesfor example, the highexpansion group-whileissuing from the other the lower expansion group and vice versa, and themeans for accomplishing this alternate action constitutes anotherfeature of the present improvements.

The manner of controlling the energy of the fluid by changing the degreeof expansion through diflerential nozzle-sections is especiallydesirable and essential where different velocities are demanded andwhere substantially the same efficiency must be maintained. The outlinedfeature is an essential inmarine work, since the physical and climaticconditions demand a variable-speed turbine with the greatest degree ofeconomy. It is to be understood that this feature, as

well as other features of my present invention, is applicable toturbines generally, although for the purpose of illustration I show anddescribe the improvements embodied in a turbine equipped especially formarine service and adapted for low and high speeds. v

The precise nature of the present improvements will now be disclosed,but only in their preferred forms of embodiment, the scope of theconcluding claims permitting the various parts and combination of partsto be variouslymodified and departed from without exceedingthe intent ofthe invention.

- In connection with the detailed description reference is to be had tothe accompanying drawings, in which Figure 1 is a side elevation of anelasticfluid turbine embodying my invention. Fig.

2 .is a vertical central longitudinal sectional view of the sameintermediately broken away. Fig. 3 is a cross-sectional view on line 3 3of Fig. 2. Fig. 4 is an enlarged sectional view on line 4 of Fig. 3.Fig. 5 is an enlarged view showing the construction and manner ofassemblage of the insertible blades or buckets for a reversible movingpart or wheel. Fig. 6 is a furtherenlarged similar view of the blades orbuckets for a non-reversible moving part or wheel. Fig. 7 is a detailview of one of the blades or buckets for a reversible moving part orwheel.

Fig. 8 is an enlarged sectional view of one of the nozzle-sections andmovable and stationary blades or buckets. Fig. 9 is an enlarged detailview of a wheel by which the control of the nozzle-sections is eflected.Fig. 10 is an enlarged sectional view of lower and higher speednozzle-sections, valves therefor, and movable and stationary blades orbuckets.

Referringto the drawings by'numerals, 1'

designates the turbine-casing, in which are a series of moving parts orwheels 2 2, fixed on a shaft 3, common to the entire series.

box 4, secured to and supported by a radially-ribbed casing-head 5, andis mounted toward its other end in a journal-box 6, supported from thebase 7. The shaft-opening in the opposite casing-head 8 is suitablypacked, as shown. The shaft terminates at its first-named end preferablywithin the j ournal-box 4 and is provided with a collar 9, forming anoil-guard to prevent the entrance of the lubricant into the interior ofthe casing. The journal-box 4 is covered by a cap 10, screwed betweenthe threadedinner ends of the ribs and serving to exclude air from thecasing-interior, as will presently be more fully explained.

The fluid-inlet 1 1 is shown in Fig. 1 and indicated by dotted lines inFig. 2. This inpoint in the turbine where the fluid loses the majorportion of its heat units and is more or less dependent upon the actionof the condenser for its kinetic effect upon the moving parts in thecondenser end. The heating? jacket serves, therefore, to'obtain thetemperatures of the fluid at the several stages while the fluid iskinetically most active,

whereas when the fluid is deprived of the major portion of its kineticenergy and is dependent upon the condenser forfurther action, it isdesirable from a standpoint of efficiency and economy to bring the fluidto as low a temperature as possible short of condensation and. within aminimum of time.

This result is accomplished by confining the heating means to the stagesnot influenced by the condenser which is connected with the fluid-outlet16. The jacket is therefore not subjected to such a low degree oftemperature as will cause condensation therein.

Neither are the stages influenced by the condenser subjected to theaction of a heating medium. To obtain the best results from theemployment of the heating-jacket, the

IIO

fluid between the inlet and chest is compelled to traverse a spiral patharound the casing, spirally-disposed partitions 17 beinginterposedbetween the walls of the casing and jacket, as shown in Fig.2. i v

The moving parts, of which there may be any number, depending uponthe.requirements, each consists of a disk 18, having balancingball-weight races or grooves at its sides, and said disks are spacedapart by hubbed wheels19, having rims 20 and keyed or otherwise fixed tothe shaft to rotate with the disks." Toward the periphery of each diskare two oppositelyefacing concentric series of blades or bucketsalternately active to effect separate the rotation of the disk inopposite directions. The blades or buckets may be formed in the disk;but I prefer to construct them separately and interchangeable and fastenthem on the disk-rim, as shown more clearly in Fig. 5. Each of theblades or buckets is provided with an inner impact-surface 21 and anouter impact-surface 22, facing a direction o posite to that of thesurface 21 and d therefrom by a segmental portion 23. The blade orbucket terminates at its outer end in a segmental portion 24 and isprovided near its inner end with a segmental portion 25, which restsagainst the periphery of the disk. The outer segmental portion 24 isprovided at its opposite edges, respectively, with agroove 26 and atongue 27, and the intermediate segmental portion 23 is similarlyequipped at its edges with a groove 28 and a tongue 29. In assembledcondition the blades or buckets are by the provision of the tongues andgrooves radially interlocked, thereby effectually resisting the straindue to centrifugal action in rotation. The blades or buckets arefastened to the disk-rim by shouldered arms or shanks 3'0, drive-fittedinto correspondinglyformed slots 31 in the disk. The shoulders 32 32 arelocated at'each side of and short of theinner end of an arm 30, with theresult that when under strain displacement by the shoulders of the metalaround the base of a slot is avoided and the shoulders alone aresubjected to strain, which tends to shear them, but which is effectuallyresisted. To prevent fracture of the dis s between the slots therein,the arms and the slots into which they are fitted are alternately ofdifferent lengths and the shouldered ends are therefore in staggeredrelation, as shown.

Fig. 6 illustrates on a larger scale blades or buckets 33, provided withsingle im actsurfaces and adapted therefore fortur ines of thenon-reversible type. The eculiar construction of the blades or buc etsby which they are caused to interlock with each other and with the diskenables them to effectually resist the strain due to the centrifugalforce created by the revolving art. Inasmuch as the blades or buckets anthe disk are drive-fitted together, the structure is renderedpractically homogeneous with no tendency to separation by-reason of theprovision for locking the blades or buckets at a plurality of points.The blades or buckets being fashioned each separately may be separatelytested for stren by insuring against fracture or and displacement inoperation.

The disks 18 extend at their'rim portions beyond the rims of thespacing-wheels 19 and between the walls of stationary chambers 34.

g theredlstortion The first disk of the ran e extends between theleft-hand wall 35 of tile first chamber34 and the wall 14 of thefluid-chest 13. In the fluid-chest wall 14 and in the right-hand wall 36of each stationary chamber are an inner set of adiabaticexpansion-nozzle sections 37 and an outer set of similar nozzle-sections38, one set being employed to effect the rotation of the moving part inone direction and the other set serving to rotate said part in the re--verse direction, as will presently more fully appear. In the wall 35 ofeach of the stationary chambers are inner and outer concentric series ofreaction blades or buckets 39, and by reference to Fig. 8 it will beseen that the construction of the movable and stationary blades orbuckets is peculiar,- being designed with reference to each other and tothe nozzle-sections to obtain the maximum efficieney in action. Theblades or buckets are of concave-convex form, and, referring to themovable impact-blades 21, it will be noted that the are which forms theconcave i mpactsurface of one blade is drawn from'a center, which isalso the center of the are forming the convex surface of thenextadjacent blade. The fluid-passage between any two blades is therefore ofuniform cross-sectional area throughout, and in said passages no fluidexpansions may take place, the expansions occurring in thenozzle-sections alone. The stationary reaction-blades 39 are formedsimilarly to the impact-blades, but face in a direction opposite to thatof the latter. Obviously the blades 39 may be formed separatelyfrom andfastened to the chamber-wall. The cross-sectional area of the passagebetween two reaction-blades is preferably substantially equal to that.between the im-- pact-blades, with the purpose of avoiding fluidexpansion and scattering and dissipation of the fluid. The convexsurfaces are formed of arcs and tangents, the tangential angles of theimpact and reaction blade surfaces coinciding in order to maintain anequal cross-sectional area throughout the passages between the impactand reaction blades. This angle of the tangential line of animpact-blade convex surface also coincides with the angle Of'the'shOrterwall of a nozzle-section 37, whereby a portion of the passage betweenthe blades 21 forms a (3011-. tinuation of, and consequentlylengthens,said nozzle-section, the line of divergence of said section beingthereby maintained. A further and very important advantage due to thestated manner of extending the nozzlesection is that the fluid impactsagainst the moving surfaces at the most desirable point namely, near thechange in direction of the passage. By this arrangement also theenergies exerted at the 'sidesof the moving disk are practicallyequal-and the rotating disk is practically balanced between the impactand reactive forces. I I v Theffluid'passes from the steam-chest l3through the outeror inner sets of nozzle-sections, dependent upon thedesired direction of rotation of themoving parts "and saidnozzle-sections deliver adiabati'call-y partially-expanded fluid againstthe. impact blades or bucketsofthe first disk. The fluid then movesagainst the blades. or buckets in the wall ofthe stationary chamber,creating a reaction effect on the disk, after which it enters thechamber, wherein it is in a normal condition. The fluid asses from thechamber throughthe nozz e-sections in the wall thereof andimpacts'against the blades or buckets of the second disk, thence entersbetween the reaction-blades, and so on through out the range of movingparts. Theparts are proportioned to allow of the larger number of thedisks receivingthe major portion ofthe kinetic energy of the fluid, andthese disks are inclosed, as hereinbefore stated, by the heating-jacket12. The remaining disks are within the influence of the condenser.Consequently the condenser action .on the fluid supplants its otherwiseexhausted the bottom of the chamber.

kinetic energy, and a'heatin -jacket at these disks is thereforeundesirab e. Thecap l0 effectually "excludes air from the condenser endof the turbine, thereby'insuring maximum efficiency of the condenser.

The stationary chambers are each divided by a continuous ring partition,40, mounted to be rotated on rollers 41, which travel on The number andpositions of the rollers will depend upon the requirements. Thepartition provides an inner annular chamber. for the fluid enter-.

ing from the inner nozzle-sections and blades or buckets and an outerannular chamber for the fluid entering from the outer nozzlesections andblades or buckets, the chambers.

being separated and non-communicating'in every position of thepartition. The partition carries outer flange-sections 42 and innerflange-sections 43, and these sections in turn carry valves respectivelynumbered 44 and 45. By reference more particularlyto Fig.

3 it will be seen that there areprovided four groups of outernozzle-sections and three groups of inner nozzle-sections, the outernozzle-sections being employed to-eifect the rotation of the movingparts in one direction and the inner nozzle-sections serving to rotatethe parts in the reverse direction. The

valves are yieldingly supported from the flange-sections throu'ghthemedium of bolts 46 and interposedcoiled springs 47. Q (See Fig. 4.) 'In'the position of thevalve's shown in Fig. 3 the first group'of outerdiametrically opposite .nozzles a a is uncoveredand bypartially'rotating the 4Q the second group of nozzles 6b is unc'overed,'the'first roup remaining open. Furtherrotatio'n oflthe-ring moves thevalves to uncover the third group a 0, and in this position all of. thegroups are open. The nozzle-sectionsof the three groups are proportionedto obtain apredetermined velocity, which is gradually reached by the,successive uncovering of the groups. Obviously the number of 'grpups andthe number of nozzlesections comprising a group may be varied accordingto requirements. To obtain a-relatively higher rotative speed of theturbine, there are provided nozzle-sec tions d d, which are uncovered bythe further movement in the same direction of the ring and valves. Insaid further movement the uncovered groups of nozzle-sections a, b, andc are closed by the ends 48 of the ad jacent valves and the openingsbetween the valves are brought into position to open the stood. In thismanner the maximum verotating the ring and valves the velocity isgradually reduced and the. turbine is not gle of the tangential line ofan impact-blade convex surface coincides with the angle of the shorterwall of a nozzle-section, whereby a portion of the passage between twoblades forms a continuation of and lengthens said nozzle-section. Thehigher de ee of en-i ergy created in the higherspee nozzle-sections d isthe result of an increase in diver- .gence of the nozzle-walls, whichincreases the fluid expansion therein and also the result oflengtheningthe entire nozzle and changing the angle of inclination to bring theangle of its shorter wall to coincide with the angle of the tangentiallines forming part of theconvex surfaces of the impact-blades. Infurther explanation of the action of the higherspeed nozzles it will beassumed, for example, 'thatthe fluid has an initial pressure of onehundred and twenty pounds absolute and that the groups of nozzlesa, b',and cin the first stage expand the pressure to one hundred pounds,thereby creating a velocity of nine hundred feet per second, which istwice the peripheral velocity of the moving part or four hundred andfifty feet per second. It will be further assumed, for example, that thehigher velocity desired for the moving part is five hundred andseventy-five feet per second, re-

higher-speed nozzle-sections, as will be under- I locity is graduallyreached, and by reversely sulting from a fluid velocity of elevenhundred and fifty per second, and to obtain this result the higher-speednozzles, which communicate with the chest supplying the other nozzles,areconstructed and arranged to expand the fluid from one hundred andtwenty pounds to, say, eighty pounds. The increased expansion for thehigher speed has the effect of reducing the numberof stages acted uponby the kinetic energy, or, in other words, the Zero-point of kinetic,energy is changed. The stages not acted upon kinetically are subjectedto windage action of the fluid, due to the influence of the condenser,and no loss in efliciency results.

Assuming that the movements of the ring and valves to uncover. the lowand high speed nozzle-sections are clockwise, to effect the reverserotation of the turbine the ring and valves are moved anticlockwise fromtheir normal or stop position and reversing nozzle-section groups e f gare successively uncovered by the valves 45, carried by the innerflange-sections 43, thereby directing the fluid to and through the innernozzle-sections, blades, and chambers. This wide range of valveadjustment is accomplished by the simple act of moving the ring 40 andvalves,

which movements are accomplished, preferably, by a'pinion 49 and asegmental rack 50 on one of the fiange-sections 42. The pinions, whichin number correspond to the number of moving parts, are housed inrecesses 51 in the casing and, preferably at one side, as illustrated inFig. 3. The showing in Fig. 2 of the valve-adjusting means at the top isfor the sake I of clearness. The pinions are commonly fixed on a shaft52, which extends beyond the casing-head and carries awheel 53, by whichit is turned A pointer 54, movable with the wheel, and afixed dial 55,suitably marked, determine the direction and extent of movement of thevalves.

By reference to Fig. 2 it will be noted that a material clearance isprovided between the surfaces of a disk and the walls of adjoiningstationary chambers. Owing to the uniform pressure of the body of fluidbetween the outlet of one nozzle-section and the inlet of theadjacentnozzle-section, there is no tenden'cy to leakage at the disks,and sufficient clearances may be provided to allow of a con siderableend thrust of the shaft and yet,

produce no friction between the surfaces. Between the inner wall 56 of astationary chamber and the rim 20 of a wheel 19 there is, however, atendency to leakage, which is avoided by providing in the wall-surfaceor rim-surface, or in both, recesses 57, forming a fluid-packed jointand creatin obstructions to the direct passage of flui between thewheel-rim and wall of the chamber.

I claim as my invention- 1. In an elastic-fluid. turbine, a moving parthaving surfaces, and a plurality of fluidnozzles alternately active tocreate and to direct with equal efficiency fluid at different velocitiesagainst said surfaces.

- 2. In an elastic-fluid variable-speed tur- 3.'I'n'an elastic-fluidturbine, a moving,

part having impact-surfaces, anda plurality of fluid-nozzles alternatelyactive to create and to direct fluid at different velocities againstsaid surfaces to move said part at different speeds which are eachapproximately one-half that of the velocity of the fluid.

4. In an elastic-fluid turbine, a heatingjacket communicating with thefluid-chest and surrounding the portion of the casing in which the fluidretains the major portion of its kinetic energy, and means for retardingthe passage of fluid through said jacket.

5. In an elastic-fluid turbine, a heatingjacket through which the fluidpasses to the chest, said jacket surrounding the portion of the casingin which the fluid retains the major portion of its kinetic energy, andmeans in said jacket forretarding thepassage of, the fluid therethrough.

6. In an elastic-fluid turbine, a heatingjacket surrounding the casing,and means for retarding, the passage of. the fluid therethrough. a I v 7In an elastic-fluid turbine, a heatingjacket in communication with thefluid inlet and chest, and means in the jacket providing a spiral pathfor the fluid;

8. In an elastic-fluid turbine, a moving part consisting of a disk and aphn'alif'y ol' radially-interlocking impact blades or buckets removablyfastened to said disk.

9. In an elastic-fluid turbine, a moving part consisting of a disk and aplurality of separately-formled interchangeable impact blades or bucketshaving means effecting their radial locking with each other and with thedisk. e

10. In an elastic-fluid turbine, a moving part consisting of a slotteddisk and a plurality of separately-formed impact blades or bucketshaving interlocking means and arms drive-fitted in said slots.

11. In an elastic-fluid turbine, a moving part consisting of a diskformed with radially-- disposed slots, and a plurality ofradially-interlocking impact blades or buckets having shouldered armsdrive-fitted in said slots.

12. In an elastic-fluid turbine, the combination of a rotatable diskhaving a plurality of radiallydisposed slots each having oppositelateral recesses located short of the slotbase, and a plurality ofseparately-formed impact blades or buckets each having a securing-armformed with opposite shoulders located short of the end thereof, saidarms fitting said slots.

13. In an elastic-fluid turbine, a rotatable disk having a plurality ofradially-disposed slots the walls of whichgare intermediately andradially recessed, and a plurality of impact blades or buckets havingsecuring-arms conforming to and fitting said recessed slots.

14. In an elastic-fluid turbine, a rotatable disk havingradially-disposed slots, and a plurality of separately-formed impactblades or buckets having tongues and grooves whereby they areinterlocked with each other and having shouldered arms interlocking withsaid slots.

15. In an elastic-fluid turbine, a rotatable disk havinradially-disposed slots, and a plurality 0% radial separately-formedinterlocking impact blades or buckets having shouldered arms engagingsaid'slots said blades or buckets beingdrive-fitted to. each other andto the disk.

16. In an elastic-fluid turbine,a section of an adiabatic nozzle, astationary fluid chamber having in one Wall reaction-surfaces and in theother Wall a second nozzle-secti on and arranged to maintain a uniformpressure between the outlet from the first-named nozzle-seotion and theinlet to the second nozale-section, and a movin part carryingimpact-surfaces and rotatab e between the firstnamed nozzle and adjacentchamber-Wall.

17. In an elastic-fluid reversible turbine, a

stationary chamber having in one wall inner and outer series of passagesand in the other I wallo' iner and outer series ofnozzles, and arotatable ring filling the. chamber horizontally and dividingit intoinner and outer fluid-passages' 18. In an elastic-fluid reversibleturbine, a

inner and outer sets of impact-surfaoes and in the opposite wall innerand outer sets of nozzles, a rotatable partition dividing the chamberand carrying flange-sections, and nozzle-controlling valves carried bysaid flange-sections.

21. In an elastic-fluid reversible turbine, a stationary fluid-chamberhaving in one Wall inner and outer sets ofimpact-surfaces and in theopposite yvall inner and outer sets of nozzles, a rotatable partitiondividing the chamber and carrying flange-sections, andnozzle-controlling valves yieldingl y carried by said flange sections. I

22. In -an elastic-fiuid reversible turbine, a

" stationary fluid-chamber having in one wall inner and outer-sets ofimpact-surfaces and in the opposite wall inner and outer sets of Inozzles, a rotatable partition dividing the chamber and carryingflange-sections, and

nozzle-controlling segmental valves carried' by said flange-sections.

23. In an elastic-fluid reversible turbine, a stationary fluid-chamber,and a roller-supported rotatable partition dividing the chamberhorizontally.

, 24. In an elastic-fluid turbine, a fluidchamber having fluid-nozzlesadapted to create difierent degrees of" energy, a ring in the chambersupported to be rotatable, segmental valves on the ring for successivelycontrolling the valves, and meansfor rotating the ring and valves.

25. In an elastic-fluid turbine, a fluidchamber having fluid-nozzlesadapted to create different degrees of energy, a ring supported to berotatable and carrying segmental flange-sections, segmental valvescarried by the flange-sections and arranged in the movement of the ringto successively control said nozzles.

26. In an elastic-fluid turbine, a stationary part, nozzles in saidpart, a ring supported to be rotatable, segmental valves on said ringand rack and pinion means for movin the ring and valves to successivelycontro said nozzles.

27. In an elastic-fluid turbine, a stationary part, nozzles in saidpart, a ring supported to be rotatable, segmental valves on said ring,rackand-pinion means for moving the ring andfvalvesto successivelycontrol said nozzles, a shaft for the pinion, awheel on the shaft, and apointer and dial for determining the movements of the valves.

28. In an elastic-fluid reversible turbine, a stationary part, aconcentric set of nozzles adapted to create different degrees of energy,a second concentric set of nozzles adapted to create different degreesof energy and to ro tate a movable part in a direction opposite to thatof the first-named set, a ring rotatable between the sets, inner andouter valves carried by the ring, rack-and-pinion means for moving thering and valves in either direction to successively control one or theother set of nozzles. I

29. In an elastic-fluid turbine, a chamber through which the fluidpasses, disks carrying impact-surfaces and rotatable at the sides of thechamber, a spacing-wheel separating the disk and extending at its rim tothe inner wall of the chamber, and fluid-recesses forming a fluid-packedj oint'between said wall and rim. v

, 30. In an elastic-fluid'turbine, a plurality I of moving parts,spacing elements for said parts, fluid-passages between said parts andmeans for preventing fluid leakage between the elements and passae-Walls.

31. In an elastie-flui turbine, a plurality of moving disks,spacing-Wheels said disks, annular fluid-passages between the disks andbeyond the spacing-Wheels, and means providing fluid-pecking between theWheel-rims and passage-Walls.

32. In an elastic-fluid turbine, a. plurality of fluid-*ohembers throughWhich the fluid passeslaterally; a plurality of disks each moving Withclearance between the sidewalls IO of two chambers, spacing-wheelsseparating I separating said disks and means providing fluid-packingbetween the wh el-rims and inner chamberwalls. In testimony whereof Ieflix my signature in presence of two witnesses.

EDWIN F. TAYLOR.

Witnesses:

EDW. W. ANSTICE, LENA B. GOODFRIEND.

